[Federal Register Volume 63, Number 168 (Monday, August 31, 1998)]
[Rules and Regulations]
[Pages 46160-46164]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-23095]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-SW-23-AD; Amendment 39-10725; AD 98-10-09]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model SA.315B, 
SA.316B, SA.316C, SA.319B, and SE.3160 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This document publishes in the Federal Register an amendment

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adopting Airworthiness Directive (AD) 98-10-09 which was sent 
previously to all known U.S. owners and operators of Eurocopter France 
Model SA.315B, SA.316B, SA.316C, SA.319B, and SE.3160 helicopters by 
individual letters. This AD requires an initial and recurring 
inspections of the blade spar for cracks. This amendment is prompted by 
an accident in which a Model SA.315B helicopter lost a main rotor 
blade. The cause of the blade failure was fatigue cracking. This 
condition, if not corrected, could result in separation of a blade and 
subsequent loss of control of the helicopter.

DATES: Effective September 15, 1998, to all persons except those 
persons to whom it was made immediately effective by priority letter AD 
98-10-09, issued on May 6, 1998, which contained the requirements of 
this amendment.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of September 15, 1998.
    Comments for inclusion in the Rules Docket must be received on or 
before October 30, 1998.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 98-SW-23-AD, 2601 Meacham Blvd., Room 663, 
Fort Worth, Texas 76137.
    The applicable service information may be obtained from American 
Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 75053-
4005, telephone (972) 641-3460, fax (972) 641-3527. This information 
may be examined at the FAA, Office of the Regional Counsel, Southwest 
Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas; or at the 
Office of the Federal Register, 800 North Capitol Street, NW., suite 
700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Mr. Shep Blackman, Aerospace Engineer, 
FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, 2601 Meacham 
Blvd., Fort Worth, Texas 76137, telephone (817) 222-5296, fax (817) 
222-5961.

SUPPLEMENTARY INFORMATION: On February 12, 1998, the FAA issued 
priority letter AD 98-04-40 (FAA Docket 98-SW-09-AD), applicable to 
Eurocopter France Model SA.315B, SA.316B, SA.316C, SA.319B, and SE.3160 
helicopters. That AD was published in the Federal Register on April 17, 
1998 (63 FR 19183). That AD requires, for blades with 400 or more hours 
time-in-service (TIS), within 25 hours TIS, inspecting each blade spar 
for cracks using a dye-penetrant method, and visually inspecting each 
blade cuff for cracks using a 10-power or higher magnifying glass. If a 
crack is discovered in either a blade spar or cuff, removal and 
replacement of the blade with an airworthy blade is required prior to 
further flight. That action was prompted by an accident in which a 
Model SA.315B helicopter lost a main rotor blade (blade) just prior to 
take-off. Although the main gearbox and the remainder of the main rotor 
assembly separated from the helicopter and passed through the cockpit, 
there were no fatalities. The cause of the blade failure was determined 
to be fatigue cracks that originated from the outboard blade-to-cuff 
attachment bolt hole and progressed through the blade spar and cuff. 
That condition, if not corrected, could result in separation of a blade 
and subsequent loss of control of the helicopter. Priority Letter AD 
98-10-09 issued May 6, 1998, superseded AD 98-04-40. AD 98-10-09 
requires the same one-time inspections as required by AD 98-04-40, but 
also requires, at intervals not to exceed 25 hours TIS, a recurring 
visual inspection of the blade spar at the outboard blade-to-cuff 
attachment bolt hole for cracks using a 10-power or higher magnifying 
glass.
    The FAA has reviewed Eurocopter France Service Telex No. 00055/
0034/98, dated February 3, 1998 (Eurocopter Service Telex: 316/319 No. 
01.64 and 315 No. 01.29), which describes procedures for inspecting 
each blade spar for cracks using a dye-penetrant method, and visually 
inspecting each blade cuff for cracks using a 10-power or higher 
magnifying glass; and Eurocopter France Service Telex No. 00060/00099/
98, dated April 9, 1998 (Eurocopter Service Telex: 316/319 No. 01.65 
and 315 No. 01.30), which describes procedures for repetitively 
inspecting each blade spar for cracks using a 10-power or higher 
magnifying glass. Additionally, the Direction Generale De L'Aviation 
Civile, which is the airworthiness authority for France, has issued AD 
98-088-055(A) and 98-089-038(A), both dated February 25, 1998; and AD 
98-170-056(A)R1 and 98-171-039(A)R1, both dated May 6, 1998, to mandate 
these actions.
    Since the unsafe condition described is likely to exist or develop 
on other Eurocopter France Model SA.315B, SA.316B, SA.316C, SA.319B, 
and SE.3160 helicopters of the same type design, the FAA issued 
priority letter AD 98-10-09 to prevent separation of a blade and 
subsequent loss of control of the helicopter. This AD requires, for 
blades with 400 or more hours time-in-service (TIS), within 25 hours 
TIS, inspecting each blade spar for cracks using a dye-penetrant 
method, and visually inspecting each blade cuff for cracks using a 10-
power or higher magnifying glass; and thereafter, visually inspecting 
each blade spar with a 10-power or higher magnifying glass at intervals 
not to exceed 25 hours TIS. If a crack is discovered in either a blade 
spar or cuff, removal and replacement of the blade with an airworthy 
blade is required prior to further flight. The actions are required to 
be accomplished in accordance with the service telexes described 
previously.
    Since it was found that immediate corrective action was required, 
notice and opportunity for prior public comment thereon were 
impracticable and contrary to the public interest, and good cause 
existed to make the AD effective immediately by individual letters 
issued on May 6, 1998 to all known U.S. owners and operators of 
Eurocopter France Model SA.315B, SA.316B, SA.316C, SA.319B, and SE.3160 
helicopters. These conditions still exist, and the AD is hereby 
published in the Federal Register as an amendment to section 39.13 of 
the Federal Aviation Regulations (14 CFR 39.13) to make it effective to 
all persons. The FAA has made two non-substantive changes to the 
Priority Letter AD which will neither increase the economic burden on 
an operator nor increase the scope of the AD. The 400 or more hours TIS 
threshold provision has been moved from the compliance paragraph to the 
applicability paragraph. Additionally, Figure 1 has been enhanced to 
provide a clearer picture of the affected blade area.
    Previous completion of the inspections required by AD 98-04-40 
constitutes compliance with the initial blade inspections required by 
this AD. The recurring visual inspections specified in this AD shall 
begin on or before 25 hours TIS after the initial inspections required 
by either this AD or AD 98-04-40, whichever occurred first. If more 
than 25 hours TIS has elapsed since the inspections required by AD 98-
04-40, then the recurring visual inspection specified in this AD must 
be accomplished prior to further flight.
    The FAA estimates that 106 helicopters of U.S. registry will be 
affected by this AD, that it will take approximately 4 work hours per 
helicopter to inspect a blade and 4 work hours to replace a main rotor 
blade, if necessary, and that the average labor rate is $60 per work 
hour. Required parts will cost approximately $49,700 per blade. Based 
on these figures, the total cost impact of the AD on U.S. operators is 
estimated to be $5,319,080

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for the first year, assuming one blade replacement per helicopter and 
$25,440 each subsequent year, assuming five inspections per year and no 
blade replacements.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an opportunity for public comment, comments are invited on 
this rule. Interested persons are invited to comment on this rule by 
submitting such written data, views, or arguments as they may desire. 
Communications should identify the Rules Docket number and be submitted 
in triplicate to the address specified under the caption ADDRESSES. All 
communications received on or before the closing date for comments will 
be considered, and this rule may be amended in light of the comments 
received. Factual information that supports the commenter's ideas and 
suggestions is extremely helpful in evaluating the effectiveness of the 
AD action and determining whether additional rulemaking action would be 
needed.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the rule. All comments submitted will be 
available, both before and after the closing date for comments, in the 
Rules Docket for examination by interested persons. A report that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this rule must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket No. 98-SW-23-AD.'' The postcard will be date stamped and 
returned to the commenter.
    The regulations adopted herein will not have substantial direct 
effects on the States, on the relationship between the national 
government and the States, or on the distribution of power and 
responsibilities among the various levels of government. Therefore, in 
accordance with Executive Order 12612, it is determined that this final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and that it is not a ``significant regulatory 
action'' under Executive Order 12866. It has been determined further 
that this action involves an emergency regulation under DOT Regulatory 
Policies and Procedures (44 FR 11034, February 26, 1979). If it is 
determined that this emergency regulation otherwise would be 
significant under DOT Regulatory Policies and Procedures, a final 
regulatory evaluation will be prepared and placed in the Rules Docket. 
A copy of it, if filed, may be obtained from the Rules Docket at the 
location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by removing Amendment 39-10479 (63 FR 
19183, April 17, 1998) and by adding a new airworthiness directive 
Amendment 39-10725 to read as follows:

AD 98-10-09  Eurocopter France: Amendment 39-10725. Docket No. 98-
SW-23-AD. Supersedes AD 98-04-40, Amendment 39-10479, Docket 98-SW-
09-AD.

    Applicability: Model SA.315B, SA.316B, SA.316C, SA.319B, and 
SE.3160 helicopters, with main rotor blades, part numbers 3160S11-
10000 all dash numbers, 3160S11-30000 all dash numbers, 3160S11-
35000 all dash numbers, 3160S11-40000 all dash numbers, 3160S11-
45000 all dash numbers, 3160S11-50000 all dash numbers, or 3160S11-
55000 all dash numbers, with 400 or more hours time-in-service 
(TIS), installed, certificated in any category.

    Note 1: This AD applies to each helicopter identified in the 
preceding applicability provision, regardless of whether it has been 
modified, altered, or repaired in the area subject to the 
requirements of this AD. For helicopters that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must use the authority 
provided in paragraph (f) to request approval from the FAA. This 
approval may address either no action, if the current configuration 
eliminates the unsafe condition, or different actions necessary to 
address the unsafe condition described in this AD. Such a request 
should include an assessment of the effect of the changed 
configuration on the unsafe condition addressed by this AD. In no 
case does the presence of any modification, alteration, or repair 
remove any helicopter from the applicability of this AD.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent separation of a blade and subsequent loss of control 
of the helicopter, accomplish the following:
    (a) Within 25 hours TIS, inspect each blade spar for cracks 
using a dye-penetrant method in accordance with paragraphs CC.1 
through CC.4 of the Operational Procedures in Eurocopter France 
Service Telex No. 00055/0034/98, dated February 3, 1998 (Eurocopter 
Service Telex: 316/319 No. 01.64 and 315 No. 01.29).
    (b) Within 25 hours TIS, visually inspect the upper and lower 
surfaces of each blade cuff for cracks, especially around the 
attachment bolts, using a 10-power or higher magnifying glass.
    (c) Within 25 hours TIS from the last required inspection of 
each blade spar for cracks in the area indicated in Figure 1, and 
thereafter at intervals not to exceed 25 hours TIS:
    (1) Without removing the blade from the helicopter, clean each 
blade root area using ``Teepol'' or an equivalent product.
    (2) Support the blade tip to eliminate blade droop while 
inspecting the lower blade surface.
    (3) Visually inspect each blade spar with a 10-power or higher 
magnifying glass along the hatched area indicated in Figure 1, 
beginning on the blade lower surface, then on the flat section of 
the trailing edge (B), on the blade upper surface, and then on the 
flat section of the leading edge (A).
    (4) Before returning the blades to service, confirm that there 
is a sealing bead (1) around the edge of the blade cuff.

    Note 2: Eurocopter France Service Telex No. 00060/00099/98, 
dated April 9, 1998 (Eurocopter Service Telex: 316/319 No. 01.65 and 
315 No. 01.30) pertains to the subject of this AD.

    (d) If more than 25 hours TIS have elapsed since the last 
required inspection of each blade spar for cracks in the area 
indicated in Figure 1, before further flight, conduct the 
inspections required by paragraph (c) of this AD.
    (e) If a crack is found in a blade spar or cuff, remove the 
blade and replace it with an airworthy blade prior to further 
flight.

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    (f) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Rotorcraft Standards Staff, 
Rotorcraft Directorate, FAA. Operators shall submit their requests 
through an FAA Principal Maintenance Inspector, who may concur or 
comment and then send it to the Manager, Rotorcraft Standards Staff.

    Note 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Rotorcraft Standards Staff.

    (g) Special flight permits will not be issued.
    (h) The inspection shall be done in accordance with paragraphs 
CC.1 through CC.4 of the Operational Procedures in Eurocopter France 
Service Telex No. 00055/0034/98, dated February 3, 1998. This 
incorporation by reference was approved by the Director of the 
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51. Copies may be obtained from American Eurocopter Corporation, 
2701 Forum Drive, Grand Prairie, Texas 75053-4005, telephone (972) 
641-3460, fax (972) 641-3527. Copies may be inspected at the FAA, 
Office of the Regional Counsel, Southwest Region, 2601 Meacham 
Blvd., Room 663, Fort Worth, Texas; or at the Office of the Federal 
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
    (i) This amendment becomes effective on September 15, 1998, to 
all persons except those persons to whom it was made immediately 
effective by Priority Letter AD 98-10-09, issued May 6, 1998, which 
contained the requirements of this amendment.

    Note 4: The subject of this AD is addressed in Direction 
Generale De L'Aviation Civile (France) AD 98-088-055(A) and 98-089-
038(A), both dated February 25, 1998; and Direction Generale De 
L'Aviation Civile (France) AD 98-170-056(A)R1 and 98-171-039(A)R1, 
both dated May 6, 1998.

    Issued in Fort Worth, Texas, on August 21, 1998.
Larry M. Kelly,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 98-23095 Filed 8-28-98; 8:45 am]
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